DSTO-TN-0498

DEF STAN 00-970 Requirements for the Design and Airworthiness of Composite Aircraft Structure

Paul J. Callus

Air Vehicles Division Platforms Sciences Laboratory

DSTO-TN-0498

ABSTRACT

One of the impediments to the introduction of composite structure into Australian Defence Force (ADF) aircraft is the difficulty in identifying those airworthiness requirements specific to these materials. The ADF uses a comparative approach where tenderers propose their own certification basis. This is assessed against the ADF comparative certification basis to ensure that all relevant issues are covered in adequate depth. The ADF comparative certification basis is DEF STAN 00-970 [2] supplemented with AAP 7001.054 [1]. This basis was reviewed. Those requirements relevant to the airworthiness of composite structure were identified and are presented in this report. The requirements for any specific composite part will likely be a sub-set of these and must be developed on a case-by-case basis.

RELEASE LIMITATION

Approved for public release

Published by DSTO Platforms Sciences Laboratory 506 Lorimer St Fishermans Bend, Victoria 3207 Australia Telephone: (03) 9626 7000 Fax: (03) 9626 7999 Commonwealth of Australia 2003 AR-012-787 June 2003 APPROVED FOR PUBLIC RELEASE

DEF STAN 00-970 Requirements for the Design

and Airworthiness of Composite Aircraft Structure

Executive Summary (U) The Australian Defence Force (ADF) maintains a keen interest in the application of composite materials to aircraft structures. The reduced weight and improved resistance to fatigue and corrosion degradation offer the potential to improve aircraft performance while reducing through-life-support costs. Many current aircraft contain significant quantities of monolithic and bonded composite material. This appears likely to increase in future acquisitions. In addition the ADF has a long history of using bonded composite repairs to support its fleet. Despite this background, virtually all of the composite structure within ADF aircraft, particularly primary structure, has been certified outside of Australia. One reason for this is the difficulty in identifying the specific set of airworthiness design requirements against which the composite structure will be certified. Currently there is no documentation that does this. The ADF airworthiness policy (Australian Air Publication 7001.054 [1]) states that contractors should submit their proposed certification basis and this will be assessed by the Commonwealth against a comparative basis. The ADF comparative basis is the UK Ministry of Defences DEF STAN 00-970 [2], supplemented with AAP 7001.054 to account for specific ADF requirements. These documents focus on traditional metallic aircraft structure, so their layout and treatment of issues is not optimised for composites. DEF STAN 00-970 and AAP 7001.054 were reviewed and, in this report, the requirements and guidance considered relevant to composite structure are collated and re-arranged into a more logical format for composites. This is the first time that the airworthiness requirements relevant to composite structure have been identified and extracted from the ADF comparative airworthiness standards. The certification requirements for any specific composite part must be developed on a case-by-case basis. The requirements identified in this report cover all possible composite structures, from a non-structural part to an entire aircraft. The requirements for any specific part will likely form a sub-set of these.

Contents

1. INTRODUCTION.............................................................................................................. 1

2. AIRWORTHINESS CERTIFICATION FOR ADF AIRCRAFT................................. 1 2.1 Contractor proposes certification basis.................................................................. 2 2.2 Acceptance of certification basis ............................................................................. 2 2.3 Contractor proposes means of demonstrating compliance ................................ 2 2.4 Acceptance of means of demonstrating compliance ........................................... 4

2.5 Contractor to demonstrate compliance .................................................................. 4 2.6 ADF acceptance........................................................................................................... 4

3. FORMAT OF THE COMPARATIVE CERTIFICATION BASIS FOR COMPOSITE STRUCTURE............................................................................................. 4

4. AIRWORTHINESS REQUIREMENTS FOR COMPOSITE AIRCRAFT STRUCTURE....................................................................................................................... 6

5. APPLICATION................................................................................................................. 52

6. DISCUSSION ................................................................................................................... 52

7. ACKNOWLEDGMENTS................................................................................................ 53

8. REFERENCES ................................................................................................................... 53

APPENDIX A: SELECTED SUMMARY OF DEF STAN 00-970/1 (AL14).................. 55

APPENDIX B: COMPARATIVE BASIS FORMATTED IN ORDER OF DEF STAN 00-970/1 (AL14) CHAPTER................................................. 87

APPENDIX C: STRUCTURE OF DEF STAN 00-970/2 .................................................. 91

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1. Introduction

The Australian Defence Force (ADF) maintains a keen interest in the application of composite materials to aircraft structures. The reduced weight and improved resistance to fatigue and corrosion degradation offer the potential to improve aircraft performance while reducing through-life-support costs. Many military aircraft currently in production contain significant quantities of monolithic and bonded composite material. The use of composites appears likely to increase in future generations of aircraft. In addition, the ADF has a long history of using bonded composite repairs to support its fleet. Despite this background, virtually all of the composite structure within ADF aircraft, particularly primary structure, has been certified outside of Australia. A contributing factor to the lack of composites certification is the difficulty in identifying the airworthiness requirements that must be met by composite structure. To address this situation the comparative airworthiness design requirements for ADF aircraft were reviewed and those sections considered relevant to composites have been extracted and collated in a format that is logical for composites.

2. Airworthiness Certification for ADF Aircraft

Significant effort and expense is required to certify metallic or composite aircraft structure. It is therefore strongly recommended that the certification issues be addressed as early as possible in any project. Policy regarding the application of airworthiness design standards within the ADF, i.e. airworthiness certification, is given in AAP 7001.054 [1]. The ADF has adopted a comparative approach where, for any acquisition or major upgrade, tenderers propose their own certification basis. In this context the term certification basis describes the complete set of airworthiness design requirements and so includes the effects of updates, improvements, special conditions or directives to standards. This proposed certification basis is assessed, by the Technical Airworthiness Regulator (TAR) or their nominated Centre of Expertise, against the ADF comparative certification basis. Any differences between the ADF and the tenderer are resolved by negotiation. The Directorate General Technical Airworthiness (DGTA) is the ADF TAR. The ADF comparative certification basis is the UK Ministry of Defence (MoD) Standard DEF STAN 00-970 [2], supplemented by Sections 2 to 4 of AAP 7001.054 to address known deficiencies in DEF STAN 00-970 when it is applied to the ADF. AAP 7001.054 states that DEF STAN 00-970 was chosen as the comparative standard because it is an accessible, comprehensive, military airworthiness standard and not because it has been judged any more, or less, safe or complete than other military or civil standards.

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Sections 2.1 to 2.6 below provide a summary of the airworthiness certification process within the ADF. 2.1 Contractor proposes certification basis

The ADF comparative certification basis is DEF STAN 00-970 supplemented with AAP 7001.054. Contractors may choose to use this as their certification basis, or propose their own. While this non-prescriptive approach permits innovative solutions, and these types of solutions are encouraged, it is the responsibility of the contractor to convince the TAR that their approach provides an equivalent level of safety to the comparative basis. In addition, the more significant the deviation from the comparative basis then the greater the time required by the TAR to review the proposal. The preferred approach is that the contractor submits their certification basis in the form of a Certification Basis Description (CBD). This provides the TAR with sufficient information to determine whether the certification basis will produce an airworthy structure. The CBD will eventually includes details of the certification requirement, verification method, conditions, verification agency and verification evidence documents, but at the initial submission it will only contain the certification requirements. An excerpt from a sample CBD is shown in Table 1. The contractor shall decide the level of detail provided in the CBD. It shall be sufficiently detailed to demonstrate that all issues have been covered, but not so detailed that it loses its effectiveness as a management tool. Ref. [1] stated that an adequately detailed CBD for an aircraft that was certified to FAR 25 would normally be achieved by numbering every section of FAR 25 (e.g. 25.1309) on a separate line of the CBD. This equates to the third order headings in the comparative certification basis shown in Table 2 or each of the items in the summary Table 3. 2.2 Acceptance of certification basis

The contractor shall negotiate the acceptance of the certification basis with the TAR and the CBD shall be modified accordingly. Ideally this process will be complete at the pre-tender stage. 2.3 Contractor proposes means of demonstrating compliance

The CBD shall be expanded to include the contractors proposed approach to demonstrate compliance with each of the certification requirements and the agency responsible for verifying compliance. The verification methods include inspection, analysis, test and similarity with parts that have received prior certification.

DSTO

-TN-04983

Table 1: Example certification basis description for composite structure

Contract clause Airworthiness requirement Design standard

Revision status

Verification

method

Conditions (Waivers,

deviations, etc)

Verification

agency

Similarity (type

details)

Verification evidence documentation (Produced by

Contractor)

General requirements DEF STAN 00-970 1.1.3-12 Issue 2 A, T Assembly specifications Operation in various climatic

regions DEF STAN 00-970 7.1.9-14 Issue 2 A, T Design report, test report

General detail design DEF STAN 00-970 4.1.2-42 Issue 2 A Design report Processes and working of

materials DEF STAN 00-970 4.6.2-14 Issue 2 A, T Design report

Manufacture, assembly and installation specifications

Precautions against corrosion and deterioration

DEFSTAN 00-970 4.3.104-116 Issue 2 I Manufacture, assembly and installation specifications

Ice protection DEF STAN 00-970 6.9.29-36 Issue 2 A. T Design report, Test report Peel Ply TAR requirement 1.1.7.1 I Manufacture and assembly

specifications

For Verification Methods: I = Inspection A = Analysis T = Test S = Similarity (Prior Clarification)

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Any airworthiness issues, judged by the TAR or Project Office (PO) to be significant enough to require recording of their resolution in the CBD, shall be the subject of an Issue Paper (IP). An IP ensures the visibility of these airworthiness issues and details all the information relevant to that issue. The reasons for raising IPs include; clarification of existing requirements, addition of new requirements, recording of proposals for wavers, deviations, special conditions or Equivalent Safety Findings (ESFs), recording of insufficient evidence to support compliance findings, or providing a mechanism to record TAR policy prior to inclusion in AAP 7001.054. The format and issuing of Issue Papers are discussed in detail in Section 1 Chapter 3 of AAP 7001.054. 2.4 Acceptance of means of demonstrating compliance

The contractor shall negotiate the acceptance of the means of demonstrating compliance with the TAR. The CBD shall be modified to record any changes. By the time the request-for-tender is released the proposed means of establishing compliance should also be specified. Again, any differences between the ADF and tenderer are to be resolved by negotiation. This resolution should be complete before any contract is entered. 2.5 Contractor to demonstrate compliance

The contractor shall demonstrate compliance to the agreed verification agency using the means agreed in the CBD. This will require the generation, review and acceptance of detailed certification submissions including test reports, generic and specific ESFs, engineering drawings, stress reports, design reports and IPs. The CBD shall be updated as compliance findings are made, by referencing the evidence that the responsible agency has made the compliance finding. 2.6 ADF acceptance

The TAR will accept the airworthiness of the composite structure when acceptable compliance findings have been made against all issues in the CBD.

3. Format of the Comparative Certification Basis for Composite Structure

This section describes the format of the certification requirements shown in Section 4 of this report and references the documents on which it is based. As with most airworthiness standards, DEF STAN 00-970 and AAP 7001.054 focus on traditional metallic structure. These documents are periodically amended and over the last thirty years a number of specific requirements and guidance regarding the use of composites have been added. However these do not cover all applicable issues.

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Therefore DEF STAN 00-970, Issue 1, Amendment 14 (DEF STAN 00-970/1 (AL14)) and AAP 7001.054(AM1) were reviewed and all requirements and guidance considered relevant to composite structure were extracted. Summaries of the extracted sections of DEF STAN 00-970/1 (AL14) and a complete listing of the Chapters are given in Appendix A. This Appendix should permit the reader to obtain an accurate reflection of the scope of this standard, plus a broad understanding of the contents of the DEF STAN 00-970/1 (AL14) requirements related to composite structure. However, for specific advice the reader must refer to the source document. The sequence and treatment of many issues in DEF STAN 00-970 originated from the certification of metallic aircraft structure and is thus not optimal for composites. The Federal Aviation Administration (FAA) Advisory Circular (AC) 20-107A [3] is widely recognised as the state-of-the-art certification document for composite materials. It describes an acceptable means of demonstrating compliance with the requirements of Federal Aviation Regulation (FAR) Part 25 [4], the FAA requirements for the airworthiness certification of transport aircraft. Almost all large civilian aircraft are certified to this requirement, or the almost identical European equivalent, Joint Aviation Regulation (JAR) Part 25 [5]. As would be expected, the format of AC 20-107A is logical and appropriate for composite structures. Thus the section headings used in AC 20-107A were used as section headings for the comparative basis shown in Section 4 of this report. However, FARs and JARs relate to civil aircraft while DEF STANs relate to military operations. The additional issues arising from military operation, or from the added responsibility that regulating, owning, operating and maintaining its aircraft places on the ADF, were added to the comparative certification basis. The requirements within each section of the comparative certification basis were divided into; general requirements, design cases, specific structures and flight testing. This is intended to simplify the formulation of, and comparison with, any proposed certification basis. To further simplify cross-referencing with DEF STAN 00-970/1, Appendix B gives the requirements of the comparative basis in order of the DEF STAN 00-970/1 Chapters. DEF STAN 00-970/1 is divided into ten parts, with each part containing Chapters and Leaflets. The Chapters define the certification requirements and it is compulsory that the proposed certification basis address all of these requirements. It is acknowledged that in some cases the requirements, as written in DEF STAN 00-970/1, will not be directly applicable to the certification of composite structure. In these cases the tenderer using the comparative certification basis in Section 4 must interpret the intention of the requirement and submit this interpretation as part of their proposed certification basis. The Leaflets supplement the Chapters by clarifying the requirements, explaining the reasoning behind requirements, and providing recommendations or advice on acceptable means of demonstrating compliance. It is therefore not compulsory to

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follow the advice given in the Leaflets. However, if guidance on any issue is given and the tenderer using this comparative basis proposes to deviate from this guidance, then a justification for the deviation should also be submitted with their proposal. DEF STAN 00-970/1 (AL14) was reissued as DEF STAN 00-970/2 [6] on 1 December 1999. This restructure was intended to enable greater flexibility and facilitate further review of DEF STAN 00-970/2. The three major features of this reissue were: 1. all requirements, apart from the requirements for fatigue and data recording

systems, were unchanged, 2. the format of the document was changed extensively. In contrast with the

Chapters and Paragraphs used in DEF STAN 00-970/1, DEF STAN 00-970/2 is presented as clauses. It is divided into nine parts, each part is divided into a maximum of nine sections, and each section divided into clauses. The clauses contain the detailed technical requirements. The structure of DEF STAN 00-970/2, in the form of an abbreviated table of contents, is shown in Appendix C.

3. the paragraphs from DEF STAN 00-970/1 (AL14) were interpreted and classified

as requirement, compliance or guidance. The clauses in DEF STAN 00-970/2 are presented under these headings.

Part 1 of DEF STAN 00-970/2, denoted DEF STAN 00-970 (PART 1)/2, details the airworthiness certification requirements for combat aircraft. The clauses from DEF STAN 00-970 (PART 1)/2, corresponding to the selected Chapters/Paragraphs from DEF STAN 00-970/1 (AL14), are included in the comparative certification basis in Section 4.

4. Airworthiness Requirements for Composite Aircraft Structure

Table 2 shows the requirements, derived from DEF STAN 00-970, AAP 7001.054 and those acknowledged in Section 7, that were identified as relevant to the airworthiness certification of composite aircraft structure. It is likely that the third order headings from Table 2 will be suitable as individual line items in a CBD. These headings are shown in Table 3.

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Table 2: Certification basis for composite aircraft structure based on the requirements of DEF STAN 00-970.

Def Stan 00-970

/1 (AL14) (Part 1) /2 Item

Chapt Para Clause

Description

1. MATERIAL AND FABRICATION DEVELOPMENT Aim: To ensure suitable, (i) design database (that includes the effects of environment and impact

on material properties), (ii) manufacture processes and (iii) assembly processes. Compliance: Typically by test. Experience with the same or similar materials/processes, results from

previous test programmes and validated analytical techniques may be used to reduce the extent of testing.

1.1 General Requirements 1.1.1 General Requirements

STANDARD ITEMS 1.1.1.1 100 2 1.1.3 Requirements of appropriate standards

INSTALLATION INFORMATION FOR ITEMS OF EQUIPMENT 1.1.1.2 100 3 1.1.4 Installation instructions

STRENGTH 1.1.1.3 100 4 1.1.5 Applicability of strength clauses

TESTS PROTOTYPE TESTS

1.1.1.4 100 6 1.1.7 Applicability and extent of prototype tests COMPONENT TESTS

1.1.1.5 100 6 1.1.8 Separate specifications for components PREVENTION OF INCORRECT ASSEMBLY OF SYSTEMS

1.1.1.6 100 7 1.1.9 Parts that may cause accidents or damage 1.1.1.7 100 7 1.1.10 Other parts 1.1.1.8 100 7 1.1.11 Fluid systems

CONDITIONS OF OPERATION 1.1.1.9 100 8 1.1.12 Function of installations and systems

1.1.2 Operation In Various Climatic Regions TEMPERATURE

1.1.2.1 101 1 7.1.9 Worldwide temperatures 1.1.2.2 101 1 7.1.10 Capability for worldwide flight 1.1.2.3 101 1 7.1.11 Landing 1.1.2.4 101 1 7.1.12 Equipment 1.1.2.5 101 1 7.1.13 Arctic testing for new types of aeroplane

HUMIDITY 1.1.2.6 101 2 7.1.14 Design humidity-temperature envelope 1.1.2.7 101 L0 S7/L0 References 1.1.2.8 101 L2 S7/L1 Operation in various climatic conditions - Standard atmospheric

conditions 1.1.2.9 101 L3 S7/L2 Operation in various climatic conditions - Temperature limits for design

purposes 1.1.2.10 101 L4 S7/L3 Operation in various climatic conditions - Humidity conditions

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Def Stan 00-970

/1 (AL14) (Part 1) /2 Item

Chapt Para Clause

Description

1.1.3 General Detail Design GENERAL

1.1.3.1 400 1 4.1.2 Minimise parts 1.1.3.2 400 1 4.1.3 Safety factor

GRADING OF PARTS AND ASSEMBLIES INTRODUCTION

1.1.3.3 400 2 4.1.4 Appropriate quality control and testing 1.1.3.4 400 2 4.1.5 Grading of standard parts

GRADING REQIUREMENTS 1.1.3.5 400 2 4.1.6 Grade A selection criteria 1.1.3.6 400 2 4.1.7 Grade B selection criteria

DRAWINGS AND QUALITY CONTROL 1.1.3.7 400 2 4.1.8 Quality control requirements on drawings 1.1.3.8 400 2 4.1.9 Additional quality control requirements

STANDARD PARTS 1.1.3.9 400 3 4.1.10 Requirements of other standards

1.1.3.10 400 3 4.1.11 Other series 1.1.3.11 400 3 4.1.12 Issue number of drawing

MATERIALS AND PROCESSES 1.1.3.12 400 4 4.1.13 Material and manufacture processes for Grade A parts 1.1.3.13 400 4 4.1.14 Specification for unapproved material or processes on Grade A parts 1.1.3.14 400 4 4.1.15 Material specifications for Grade B parts

STRENGTH OF MATERIALS 1.1.3.15 400 5 4.1.16 Guidance regarding strength of defined materials

LOCKING OF THREADED FASTENERS 1.1.3.16 400 7 4.1.18 Standard of locking 1.1.3.17 400 7 4.1.19 Grade A applications 1.1.3.18 400 7 4.1.20 Grade B applications 1.1.3.19 400 7 4.1.21 Locking wire 1.1.3.20 400 7 4.1.22 Centre popping 1.1.3.21 400 7 4.1.23 Peening 1.1.3.22 400 7 4.1.24 Locking adhesives 1.1.3.23 400 7 4.1.25 End protrusion 1.1.3.24 400 7 4.1.26 Damage to protective treatment

USE OF COLD FORGED STEEL BOLTS 1.1.3.25 400 9 4.1.28 Specification for cold forged steel bolts

CONTROLLED TIGHTENING OF BOLTS OPERATIONAL REQUIREMENTS 1.1.3.26 400 12 4.1.34 Scope of application 1.1.3.27 400 12 4.1.35 Bolt elongation technique 1.1.3.28 400 12 4.1.36 Access for torque loading tools

SAFETY REQUIREMENTS 1.1.3.29 400 12 4.1.37 Requirements for drawings 1.1.3.30 400 12 4.1.38 Lubricant compatibility 1.1.3.31 400 12 4.1.39 Effect of hot joints on torque upon re-assembly

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Def Stan 00-970

/1 (AL14) (Part 1) /2 Item

Chapt Para Clause

Description

REDUCTION OF VULNERABILITY TO BATTLE DAMAGE 1.1.3.32 400 13 4.1.40 Material repairability and resistance to Nuclear, Biological and Chemical

(NBC) attack 1.1.3.33 400 13 4.1.41 Repairable materials 1.1.3.34 400 13 4.1.42 Response to NBC effects 1.1.3.35 400 L1 S4/L1 General detail design - Grading of aeroplane parts and assemblies

1.1.4 Processes And Working Of Materials JOINTING PROCESSES

1.1.4.1 402 1 4.6.2 Grading of joints made by metallic jointing processes STRENGTH AFTER PROCESSING DETAIL DRAWINGS

1.1.4.2 402 2 4.6.3 Documentation requirements for process dependant joints 1.1.4.3 402 2 4.6.4 Properties for welded joints

FLAW DETECTION 1.1.4.4 402 4 4.6.6 Need for flaw detection

ADHESIVE BONDING 1.1.4.5 402 6 4.6.10 Validation of Grade A components

SEALANTS AND SEALING 1.1.4.6 402 7 4.6.11 Specification for sealing processes 1.1.4.7 402 7 4.6.12 Ensure appropriate pre-treatment on surfaces to be sealed 1.1.4.8 402 7 4.6.13 Leak resistance 1.1.4.9 402 7 4.6.14 Consideration of concentrated loads

1.1.4.10 402 L0 S4/L0 References 1.1.4.11 402 L2 S4/L16 Processes and working of materials - Adhesive bonding of structural parts

process and control 1.1.4.12 402 L3 S4/L17 Processes and working of materials - Adhesive bonding of structural parts

recommended design practice 1.1.4.13 402 L7 S4/L20 Processes and working of materials - Sealants and sealing

1.1.5 Precautions Against Corrosion And Deterioration PRECAUTIONS AND TREATMENTS DURING ASSEMBLY FIELD OF APPLICATION

1.1.5.1 409 24 4.3.104 Scope of requirement WET ASSEMBLY

1.1.5.2 409 24 4.3.105 Requirement for static joints 1.1.5.3 409 24 4.3.106 Sealants 1.1.5.4 409 24 4.3.107 Jointing compounds

MATERIALS APPROVED FOR WET ASSEMBLY 1.1.5.5 409 24 4.3.108 Preferred sealant for fuel tanks, cabin skins and pressure capsules 1.1.5.6 409 24 4.3.109 Acceptable jointing compounds

EXCEPTIONS AND SPECIAL CASES 1.1.5.7 409 24 4.3.110 Spot and seam welds 1.1.5.8 409 24 4.3.111 Adhesive bonded joints 1.1.5.9 409 24 4.3.112 Screwed unions in liquid and gaseous systems

1.1.5.10 409 24 4.3.113 Lubricated joints 1.1.5.11 409 24 4.3.114 Joints with anti-fretting treatments

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Def Stan 00-970

/1 (AL14) (Part 1) /2 Item

Chapt Para Clause

Description

NON-METALLIC SHIMMING AND PACKING MATERIALS 1.1.5.12 409 24 4.3.115 Material selection and assembly requirements

METAL SHIMS 1.1.5.13 409 24 4.3.116 Assembly of sacrificial metal shims

1.1.6 Ice Protection DESIGN AND CONSTRUCTION

1.1.6.1 712 8 6.9.29 Requirements for ice protection system 1.1.6.2 712 8 6.9.30 Strength and fatigue damage tolerance requirements 1.1.6.3 712 8 6.9.31 Requirements for the design of electrical installations 1.1.6.4 712 8 6.9.32 Material requirements 1.1.6.5 712 8 6.9.33 Temperature limiting devices 1.1.6.6 712 8 6.9.34 Insulation 1.1.6.7 712 8 6.9.35 External supplies or equipment for ground tests 1.1.6.8 712 8 6.9.36 Diameter of filling orifices

1.1.7 Peel Ply 1.1.7.1 ADF TAR requirement - Peel ply

Where peel plies are used on composite surfaces that are to be bonded, the surfaces must be abraded prior to bonding. Light grit blasting is the preferred method of abrasion. Coated peel plies should not be used.

1.2 Specific Structures 1.2.1 Precautions Against Corrosion And Deterioration

TREATMENT OF RADOMES 1.2.1.1 409 22 4.3.102 Effect of materials on radar transparency

1.2.2 Attachment To Sandwich Structures 1.2.2.1 ADF TAR requirement - Attachment to sandwich structure

No fabrication, assembly or marking process shall penetrate sandwich structures.

2. PROOF OF STRUCTURE - STATIC Aim: To ensure sufficient static strength of the structure. Compliance: Typically through a series of ultimate load tests at the appropriate

coupon/element/subcomponent/full-scale level giving due regard to service environment and degradation resulting from manufacture and service. Validated analytical techniques may be used to reduce the extent of testing.

2.1 General Requirements 2.1.1 General Requirements

STRENGTH 2.1.1.1 100 4 1.1.5 Applicability of strength clauses

TESTS PROTOTYPE TESTS

2.1.1.2 100 6 1.1.7 Applicability and extent of prototype tests COMPONENT TESTS

2.1.1.3 100 6 1.1.8 Separate specifications for components

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Def Stan 00-970

/1 (AL14) (Part 1) /2 Item

Chapt Para Clause

Description

2.1.2 Static Strength And Deformation 2.1.2.1 200 1 3.1.1 Scope of the section 2.1.2.2 200 1 3.1.2 Identification of critical design cases 2.1.2.3 200 1 3.1.3 Allowables for Grade A details 2.1.2.4 200 1 3.1.4 Requirements for ultimate and proof loads

DESIGN CASES 2.1.2.5 200 2 3.1.5 Tracing of load paths

THE ULTIMATE STRENGTH AND PROOF REQUIREMENTS 2.1.2.6 200 3 3.1.6 Effects of proof loads 2.1.2.7 200 3 3.1.7 Effects of ultimate load

SUBSTANTIATION OF THE STATIC ALLOWABLE STRESS FOR GRADE A DETAILS 2.1.2.8 200 4 3.1.7 Dimensions for determination of allowables 2.1.2.9 200 4 3.1.8 Loading and environment for determining allowables

2.1.2.10 200 4 3.1.9 Basis of strength derivation METHOD OF STRUCTURAL ANALYSIS 2.1.2.11 200 4 3.1.10 Substantiation of method of structural analysis

DEMONSTRATION OF COMPLIANCE WITH THE ULTIMATE STRENGTH & PROOF REQUIREMENTS FOR COMPLETE STRUCTURE OR COMPONENTS 2.1.2.12 200 5 3.1.11 Use of test factors

MEASUREMENT OF LOADS ON AEROPLANE STRUCTURES 2.1.2.13 200 6 3.1.12 Extent of test measurement of loads and temperatures

ENGINE AND AUXILIARY POWER UNIT MOUNTING LOADS 2.1.2.14 200 8 3.1.13 Strength and rigidity requirements for mountings

REDUCTION OF VULNERABILITY TO BATTLE DAMAGE 2.1.2.15 200 9 3.1.14 Design approach 2.1.2.16 200 9 3.1.15 Provision of drain holes and drip fences

CONSIDERATIONS IN SETTING PERMISSIBLE FLIGHT LOADS FOR EXPERIMENTAL AND PROTOTYPE AEROPLANES 2.1.2.17 200 10 3.1.16 Factors to be considered when determining restrictions 2.1.2.18 200 L1 S3/L1 Static strength and deformation - Principles underlying the requirements 2.1.2.19 200 L2 S3/L2 Static strength and deformation - Static structural strength test load

sequence 2.1.2.20 200 L3 S3/L3 Static strength and deformation - Engine and auxiliary power unit

mounting loads 2.1.2.21 200 L4 S3/L4 Static strength and deformation - Strength of structures under conditions

of heating and cooling 2.1.2.22 200 L5 S3/L5 Static strength and deformation - Considerations in setting permissible

flight loads for experimental and prototype aeroplanes

2.1.3 General Detail Design GENERAL

2.1.3.1 400 1 4.1.2 Minimise parts 2.1.3.2 400 1 4.1.3 Safety factor

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Def Stan 00-970

/1 (AL14) (Part 1) /2 Item

Chapt Para Clause

Description

GRADING OF PARTS AND ASSEMBLIES INTRODUCTION

2.1.3.3 400 2 4.1.4 Appropriate quality control and testing 2.1.3.4 400 2 4.1.5 Grading of standard parts

GRADING REQIUREMENTS 2.1.3.5 400 2 4.1.6 Grade A selection criteria 2.1.3.6 400 2 4.1.7 Grade B selection criteria

DRAWINGS AND QUALITY CONTROL 2.1.3.7 400 2 4.1.8 Quality control requirements on drawings 2.1.3.8 400 2 4.1.9 Additional quality control requirements

STANDARD PARTS 2.1.3.9 400 3 4.1.10 Requirements of other standards

2.1.3.10 400 3 4.1.11 Other series 2.1.3.11 400 3 4.1.12 Issue number of drawing

MATERIALS AND PROCESSES 2.1.3.12 400 4 4.1.13 Material and manufacture processes for Grade A parts 2.1.3.13 400 4 4.1.14 Specification for unapproved material or processes on Grade A parts 2.1.3.14 400 4 4.1.15 Material specifications for Grade B parts

STRENGTH OF MATERIALS 2.1.3.15 400 5 4.1.16 Guidance regarding strength of defined materials

LOCKING OF THREADED FASTENERS 2.1.3.16 400 7 4.1.18 Standard of locking 2.1.3.17 400 7 4.1.19 Grade A applications 2.1.3.18 400 7 4.1.20 Grade B applications 2.1.3.19 400 7 4.1.21 Locking wire 2.1.3.20 400 7 4.1.22 Centre popping 2.1.3.21 400 7 4.1.23 Peening 2.1.3.22 400 7 4.1.24 Locking adhesives 2.1.3.23 400 7 4.1.25 End protrusion 2.1.3.24 400 7 4.1.26 Damage to protective treatment

USE OF COLD FORGED STEEL BOLTS 2.1.3.25 400 9 4.1.28 Specification for cold forged steel bolts

CONTROLLED TIGHTENING OF BOLTS OPERATIONAL REQUIREMENTS 2.1.3.26 400 12 4.1.34 Scope of application 2.1.3.27 400 12 4.1.35 Bolt elongation technique 2.1.3.28 400 12 4.1.36 Access for torque loading tools

SAFETY REQUIREMENTS 2.1.3.29 400 12 4.1.37 Requirements for drawings 2.1.3.30 400 12 4.1.38 Lubricant compatibility 2.1.3.31 400 12 4.1.39 Effect of hot joints on torque upon re-assembly 2.1.3.32 400 L1 S4/L1 General detail design - Grading of aeroplane parts and assemblies

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2.1.4 Protection From The Effects Of Nuclear Explosions, Laser Weapons, Chemical And Biological Warfare Agents

INTRODUCTION 2.1.4.1 723 1 9.11.1 Applicability of clauses 2.1.4.2 723 1 9.11.2 Requirements for NBC/laser hardening 2.1.4.3 723 1 9.11.3 Security classification of references

NUCLEAR ENVIRONMENT REQUIREMENTS GENERAL

2.1.4.4 723 3 9.11.6 Aim of basis nuclear survivability DESIGN

2.1.4.5 723 3 9.11.7 Design objective for nuclear hardening 2.1.4.6 723 3 9.11.8 Principal design aim 2.1.4.7 723 3 9.11.9 Initial feasibility study 2.1.4.8 723 3 9.11.10 Consideration of effects of friendly forces weapons

OPERATIONAL CONDITIONS 2.1.4.9 723 3 9.11.11 Flight and ground conditions at exposure

2.1.4.10 723 L2 S9/L25 Protection from the effects of nuclear explosions, laser weapons, chemical and biological warfare agents - Nuclear weapon effects on aeroplanes

2.2 Design Cases 2.2.1 Symmetric Manoeuvres

2.2.1.1 202 1 3.3.1 Scope of clause FACTORS

2.2.1.2 202 2 3.3.2 Proof and ultimate factors for structure THE FLIGHT ENVELOPE

2.2.1.3 202 3 3.3.3 Definition of design flight envelope MANOEUVRES TO BE CONSIDERED STEADY PITCHING VELOCITY

2.2.1.4 202 4 3.3.4 Consideration of effects of steady pitching velocity PITCHING ACCELERATION

2.2.1.5 202 4 3.3.5 Consideration of loads arising from sudden positive pitch 2.2.1.6 202 4 3.3.6 Consideration of loads arising from transient pitching

SUPPLEMENTARY CONDITIONS AND ASSUMPTIONS ENGINE POWER

2.2.1.7 202 5 3.3.7 Consideration of effects of all likely engine power conditions HIGH LIFT DEVICES, AIRBRAKES AND UNDERCARRIAGE

2.2.1.8 202 5 3.3.8 Consideration of position of high lift devices 2.2.1.9 202 5 3.3.9 Consideration of effect of airbrakes

2.2.1.10 202 5 3.3.10 Consideration of effect of undercarriage position PITCHING MOMENT COEFFICIENT 2.2.1.11 202 5 3.3.11 Calculation of pitching moment coefficient and aerodynamic centre

OTHER AERODYNAMIC COEFFICIENTS AND DERIVATIONS 2.2.1.12 202 5 3.3.12 Basis of aerodynamic coefficients and derivatives

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MASS AND MASS DISTRIBUTION 2.2.1.13 202 5 3.3.13 Ranges of mass to be considered 2.2.1.14 202 5 3.3.14 Tolerance on centre of gravity position 2.2.1.15 202 L0 S3/L0 References 2.2.1.16 202 L1 S3/L7 Symmetric manoeuvres - The calculation of the response of an aeroplane

to pitch control input and associated loads when a conventional control system is used

2.2.1.17 202 L2 Part 0 Procedures for use, content and definitions 2.2.1.18 202 L3 S3/L8 Symmetric manoeuvres - The calculation of the loads associated with

symmetric manoeuvres for aeroplanes having control system with load limiting devices

2.2.2 Asymmetric Manoeuvres 2.2.2.2 203 1 3.4.1 Scope of the clause

FACTORS 2.2.2.3 203 2 3.4.2 Proof and ultimate factors for the structure

MANOEUVRES TO BE CONSIDERED 2.2.2.4 203 3 3.4.3 Manoeuvres to be considered in aeroplanes with load limiting devices 2.2.2.5 203 3 3.4.4 Manoeuvres to be considered in conventional aeroplanes

YAWING MANOEUVRES DESIGN CONDITIONS

2.2.2.6 203 4 3.4.5 Design conditions DESIGN CASES

2.2.2.7 203 4 3.4.6 Determination of loads and deflections of yaw motivator(s) 2.2.2.8 203 4 3.4.7 Consideration of deflection with sinusoidal pilot input 2.2.2.9 203 4 3.4.8 Consideration of deflections from automatic control system

CROSS COUPLING CONSIDERATIONS 2.2.2.10 203 4 3.4.9 Assumed corrective action for design cases

LONGITUDINAL STABILISER/CONTROL SURFACE LOADS 2.2.2.11 203 4 3.4.10 Considerations in calculating loads

EFFECTS OF ASYMMETRIC ENGINE FAILURE 2.2.2.12 203 5 3.4.11 Design of multi-engined aeroplanes

ROLLING MANOEUVRES 2.2.2.13 203 6 3.4.12 Context for selection of rolling manoeuvres 2.2.2.14 203 6 3.4.13 Considerations of maximum roll inceptor inputs

COMBINED PITCHING AND ROLLING 2.2.2.15 203 7 3.4.14 Consideration of effect of combined pitching and rolling

BOMB BAY AND DOOR LOADS 2.2.2.16 203 8 3.4.15 Considerations for structure related to bomb bays

MASS AND MASS DISTRIBUTION 2.2.2.17 203 9 3.4.16 Definition of masses and centre of gravity positions to be considered

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AERODYNAMIC COEFFICIENTS AND DERIVATIVES 2.2.2.18 203 10 3.4.17 Basis of aerodynamic coefficients and derivatives 2.2.2.19 203 L0 S3/L0 References 2.2.2.20 203 L1 S3/L9 Asymmetric manoeuvres - Yawing, sideslipping and rolling motions 2.2.2.21 203 L2 S3/L10 Asymmetric manoeuvres - The calculation of the loads associated with

asymmetric manoeuvres for aeroplanes having control system with load limiting devices

2.2.3 Gust Loads 2.2.3.1 204 1 3.5.1 Applicability

GENERAL 2.2.3.2 204 1 3.5.2 General requirement

FACTORS 2.2.3.3 204 2 3.5.3 Definition of design and ultimate factors for gust cases

DESIGN CONDITIONS 2.2.3.4 204 3 3.5.4 Conditions under which strength must be demonstrated 2.2.3.5 204 3 3.5.5 Case for aircraft fitted with terrain following radar

DISCRETE GUST CASES 2.2.3.6 204 4 3.5.6 Agreement regarding gust velocities to be used

SUBSONIC FLIGHT 2.2.3.7 204 4 3.5.7 Gust velocities for subsonic flight

GUST LOADS THROUGHOUT THE SPEED RANGE 2.2.3.8 204 4 3.5.8 Requirements for determining gust loads throughout the envelope

DESIGN ANALYSIS 2.2.3.9 204 5 3.5.9 Requirement for dynamic analysis

2.2.3.10 204 5 3.5.10 Determination of effects of structural flexibility on stress 2.2.3.11 204 L0 S3/L0 References 2.2.3.12 204 L1 S3/L11 Gust loads - Safe speeds for aeroplanes flying in turbulent weather 2.2.3.13 204 L2 S3/L12 Gust loads - A method of calculating gust loads for preliminary design

purposes

2.2.4 Spinning And Spin Recovery 2.2.4.1 207 1 3.8.1 Scope of requirements

STRENGTH REQUIREMENTS FACTORS

2.2.4.2 207 2 3.8.2 Requirements for ultimate and proof factors DESIGN CONDITIONS

2.2.4.3 207 2 3.8.3 Spinning conditions for design calculations 2.2.4.4 207 2 3.8.4 Full scale spinning tests

ASSOCIATED CONDITIONS 2.2.4.5 207 2 3.8.5 Engine conditions in departure phase 2.2.4.6 207 2 3.8.6 Engine conditions in other phases 2.2.4.7 207 2 3.8.7 Conditions for aeroplanes with external stores

2.3 Specific Structures 2.3.1 High Lift Devices And Airbrakes

2.3.1.1 205 1 3.6.1 Scope of the requirements

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FACTORS 2.3.1.2 205 2 3.6.2 Requirements for ultimate and proof factors

HIGH LIFT DEVICES OPERATION DURING TAKE-OFF, APPROACH AND LANDING

2.3.1.3 205 3 3.6.4 Capability of operating mechanisms for high lift devices OPERATION EN-ROUTE OR IN COMBAT

2.3.1.4 205 3 3.6.5 Capability of operating mechanisms under specified conditions RAISING SPEED

2.3.1.5 205 3 3.6.6 Prevention of excessive sinking when flaps are being retracted DESIGN AND LIMITING SPEEDS

2.3.1.6 205 3 3.6.7 Design range to allow for speed variations 2.3.1.7 205 3 3.6.8 Lower limits on design speed

STRENGTH 2.3.1.8 205 3 3.6.9 Strength requirements when high lift devices are retracted 2.3.1.9 205 3 3.6.10 Load cases when high lift devices used for takeoff, approach and landing

2.3.1.10 205 3 3.6.11 Engine conditions for all phases of flight 2.3.1.11 205 3 3.6.12 Gust, manoeuvre and other additional load considerations 2.3.1.12 205 3 3.6.13 Load cases for high lift devices used en-route or in combat

MECHANICAL INTERCONNECTION 2.3.1.13 205 3 3.6.14 Requirement for synchronised deployment 2.3.1.14 205 3 3.6.15 Proof and ultimate factors arising from failure 2.3.1.15 205 3 3.6.16 Strength of interconnection under asymmetric engine operations

CIRCUIT STIFFNESS 2.3.1.16 205 3 3.6.17 Limits on differential deployment due to circuit flexibility

AIRBRAKES 2.3.1.17 205 4 3.6.18 Time requirements for extension and retraction 2.3.1.18 205 4 3.6.19 Conditions for safe operation

STRENGTH 2.3.1.19 205 4 3.6.20 Strength requirements

MECHANICAL INTERCONNECTIONS 2.3.1.20 205 4 3.6.21 Proof and ultimate factors on critical interconnections

2.3.2 Active Control Systems 2.3.2.1 208 1 3.10.1 Scope

GENERAL REQUIREMENTS INTEGRATED SYSTEMS

2.3.2.2 208 1 3.10.2 Effects of associated systems on integrity of full-time ACS APPLICATIONS

2.3.2.3 208 1 3.10.3 Aim of full-time ACS FUNCTIONAL REQUIREMENTS

2.3.2.4 208 1 3.10.4 Performance requirements AIRFRAME ASPECTS GENERAL

2.3.2.5 208 4 3.10.54 Guidance regarding interaction between airframe and ACS design

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STRUCTURAL IMPLICATIONS 2.3.2.6 208 4 3.10.55 Factors for consideration when determining structural integrity 2.3.2.7 208 4 3.10.56 Limit load cases following ACS failure 2.3.2.8 208 4 3.10.57 Failure warning system

INTEGRITY OF THE ACTIVE CONTROL SYSTEM 2.3.2.9 208 4 3.10.58 Structural weight/reliability considerations

DESIGN CASES 2.3.2.10 208 4 3.10.59 Principles for deriving critical design load cases

LOADS MEASUREMENT 2.3.2.11 208 4 3.10.60 Requirements for prototype, development and preproduction aeroplanes 2.3.2.12 208 4 3.10.61 Requirements for in-service aeroplanes

MODIFICATIONS TO SOFTWARE AND HARDWARE 2.3.2.13 208 4 3.10.62 Requirements for approval of changes to ACS software or hardware

APPLICATIONS INTRODUCTION 2.3.2.14 208 7 3.10.94 Saturation characteristics of flight critical systems 2.3.2.15 208 7 3.10.95 Compatibility of systems 2.3.2.16 208 7 3.10.96 Requirements for systems which allow selection of the control mode 2.3.2.17 208 7 3.10.97 Provision for pilot override

ACTIVE FLUTTER CONTROL (AFC) 2.3.2.18 208 7 3.10.98 Aim of the system 2.3.2.19 208 7 3.10.99 Requirement to recover following failure of AFC

MANOEUVRE LOAD ALLEVIATION (MLA) 2.3.2.20 208 7 3.10.100 Requirement for effect of MLA on structural integrity

GUST LOAD ALLEVIATION (GLA) 2.3.2.21 208 7 3.10.101 To be completed

WING CAMBER CONTROL (WCC) 2.3.2.22 208 7 3.10.102 Recovery requirements

STALL AND SPIN PREVENTION (SSP) 2.3.2.23 208 7 3.10.103 Determination of post departure and recovery characteristics

STRUCTURAL LOAD LIMITING (SLL) 2.3.2.24 208 7 3.10.104 Requirement for pilot control

VARIABLE CONFIGURATION CONTROL (VCC) 2.3.2.25 208 7 3.10.105 Requirement for failsafe reversion to manual control 2.3.2.26 208 7 3.10.106 Presentation of configuration data to pilot

RIDE CONTROL (RC) 2.3.2.27 208 7 3.10.107 Compliance requirements and guidance on aim of requirement 2.3.2.28 208 L4 S3/L28 Structural implications of ACS

2.3.3 Radomes MECHANICAL/REQUIREMENTS

2.3.3.1 210 1 6.1.31 Constraints on radome shape 2.3.3.2 210 2 6.1.32 Structural requirements 2.3.3.3 210 L0 S6/L0 References

2.3.4 Radio And Radar Installations 2.3.4.1 708 1 6.1.1 Scope

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RADIO AND RADAR EQUIPMENTS 2.3.4.2 708 1 6.1.2 Performance of installations 2.3.4.3 708 1 6.1.3 Proof and ultimate factors

AERIAL DESIGN 2.3.4.4 708 2 6.1.18 Electrical performance considerations 2.3.4.5 708 2 6.1.19 Mechanical performance considerations

AERIAL INSTALLATION ON AN AIRFRAME 2.3.4.6 708 4 6.1.23 Conductivity considerations for mounting flanges 2.3.4.7 708 4 6.1.24 Weak link in fixed wire aerials 2.3.4.8 708 4 6.1.25 Drainage and prevention of moisture ingress 2.3.4.9 708 4 6.1.26 Aerials through pressure diaphragms

2.3.4.10 708 4 6.1.27 Pressure sealing for aerials 2.3.4.11 708 4 6.1.28 Retractable aerial mountings 2.3.4.12 708 4 6.1.29 Effect of single failure on aerial systems 2.3.4.13 708 4 6.1.30 Interlocks to prevent simultaneous transmissions

RADOMES AND AERIAL FAIRINGS MECHANICAL/REQUIREMENTS 2.3.4.14 708 5 6.1.31 Radome shape 2.3.4.15 708 5 6.1.32 Structural soundness of radomes 2.3.4.16 708 5 6.1.33 Lightning protection of radome fairings

ELECTRICAL REQUIREMENTS 2.3.4.17 708 5 6.1.34 Transmissivity of radomes 2.3.4.18 708 5 6.1.35 Protection from high energy transmissions

TESTING 2.3.4.19 708 9 6.1.47 Conduct of flight and ground testing 2.3.4.20 708 L0 S6/L0 References

2.3.5 Armament Installations INTRODUCTION

2.3.5.1 711 1 9.1.1 Scope 2.3.5.2 711 1 9.1.2 Approval requirements 2.3.5.3 711 1 9.1.3 Safety and reliability with cameras, tone control and training aids

GENERAL SAFETY AND RELIABILITY STRENGTH & ENVRONMENTAL CONDITIONS

2.3.5.4 711 3 9.1.9 Strength and stiffness requirements 2.3.5.5 711 3 9.1.10 Function of armament system under defined environment

OPERATION OF WEAPON BAY DOORS 2.3.5.6 711 15 9.1.60 Considerations to allow operation of weapon bay doors

INSTALLATION 2.3.5.7 711 20 9.1.4 Prevention of fouling and safety from single failure

2.3.6 Pressure Cabins 2.3.6.1 716 1 3.7.1 Scope

DIFFERENTIAL PRESSURE REQUIREMENTS DEFINITIONS

2.3.6.2 716 2 3.7.2 Definition of low and high pressure differential systems

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LOW DIFFERENTIAL PRESSURE SYSTEMS 2.3.6.3 716 2 3.7.3 Pressure requirements 2.3.6.4 716 2 3.7.4 Tolerance on pressure level

HIGH DIFFERENTIAL PRESSURE SYSTEMS 2.3.6.5 716 2 3.7.5 Pressure differential requirements 2.3.6.6 - - 3.7.6 Capability for crew selection of pressure altitude 2.3.6.7 - - 3.7.7 Tolerance on pressure level 2.3.6.8 - - 3.7.8 Rate of change of pressure level

TEST CONNECTIONS 2.3.6.9 716 10 3.7.35 Use of standard connections

STRENGTH OF PRESSURE CABIN 2.3.6.10 716 11 3.7.36 Two pressures to be considered 2.3.6.11 716 11 3.7.37 Proof and ultimate factors for defined loads 2.3.6.12 716 11 3.7.38 Proof and ultimate factors for alternate defined loads

STATIC STRENGTH OF PRESSURISATION SYSTEM 2.3.6.13 716 13 3.7.40 Proof and ultimate factors for components, pipes and ducting 2.3.6.14 716 13 3.7.41 Proof and ultimate factors following blockage by component failure

PROVING TEST 2.3.6.15 716 14 3.7.42 All cabins to be proof tested before delivery

STATIC TEST 2.3.6.16 716 14 3.7.43 Tests to support design calculations 2.3.6.17 716 14 3.7.44 Test to support design calculations for components 2.3.6.18 716 L1 S3/L13 Pressure cabins - Strength testing

2.4 Flight Testing 2.4.1 General Flight Test Requirements - Systems And Structures

2.4.1.1 1000 1 1.2.1 Scope 2.4.1.2 1000 2 Deleted

APPLICABILITY 2.4.1.3 1000 3 1.2.2 Applicability of tests 2.4.1.4 1000 3 1.2.3 Standard of systems

LOADING 2.4.1.5 1000 5 1.2.7 Loading and centre of gravity requirements for tests

GENERAL TEST CONDITIONS 2.4.1.6 1000 6 1.2.8 Location of specifications for each test clause

TESTS 2.4.1.7 1000 7 1.2.9 Responsibility for conducting flight tests 2.4.1.8 1000 7 1.2.10 Specification of limitations prior to flight testing

2.4.2 Structures FLIGHT TESTING

2.4.2.1 1015 1 3.1.17 Scope BASIC REQUIREMENTS

2.4.2.2 1015 2 3.1.18 Agreement on scope of load measurement programme 2.4.2.3 1015 2 3.1.19 Co-ordination of load measurement programme

APPLICABILITY 2.4.2.4 1015 3 3.1.20 Type of aeroplane on which tests are to be conducted

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TEST REQUIREMENTS 2.4.2.5 1015 4 3.1.21 Required measurements and conditions 2.4.2.6 1015 4 3.1.22 Demonstration of structural strength

MEASUREMENTS 2.4.2.7 1015 5 3.1.23 Number and location of measurement points 2.4.2.8 1015 5 3.1.24 Temperature measurement 2.4.2.9 1015 5 3.1.25 Measurement of aeroelastic distortion and modes of vibration

2.4.2.10 1015 5 3.1.26 Recording of flight parameters FLIGHT LIMITATIONS AND THE RELATION BETWEEN STATIC STRENGTH TESTS AND FLIGHT TESTS 2.4.2.11 1015 6 3.1.27 Phasing of flight and static strength programmes 2.4.2.12 1015 6 3.1.28 Limitations for flight testing developmental aeroplanes 2.4.2.13 1015 6 3.1.29 Adjustment of ground testing on basis of flight test measurements 2.4.2.14 1015 6 3.1.30 Incorporation of structural alterations fund necessary from static tests 2.4.2.15 1015 6 3.1.31 Timing of tests required in 3.1.22 2.4.2.16 1015 L1 S3/L6 General information

3. PROOF OF STRUCTURE - DAMAGE/FATIGUE TOLERANCE Aim: To ensure that the structure can withstand the effects of repeated loading for the design

service life. Compliance: Typically by the validation of a no-flaw-growth approach. This may be done by test, analysis

or experience with similar designs. The effects of environment, damage, loading and inspection shall be addressed. Validated analytical techniques may be used to reduce the extent of testing.

3.1 General Requirements 3.1.1 Fatigue Damage Tolerance

3.1.1.1 201 1 Nil Introduction 201 2 Nil Safe-life details 201 3 Nil Inspection-dependant details 201 4 Nil Service monitoring 201 5 Nil Demonstration of compliance 201 6 Nil Compliance of aeroplanes not designed to DEF STAN 00-970 201 7 Nil Definitions

3.1.1.2 Nil Nil 3.2.1 Scope APPROACH

3.1.1.3 Nil Nil 3.2.2 Acceptable tolerance to damage and defects 3.1.1.4 Nil Nil 3.2.3 Acceptable safe life 3.1.1.5 Nil Nil 3.2.4 Exclusions to safe life approach 3.1.1.6 Nil Nil 3.2.4 Requirements for residual strength 3.1.1.7 Nil Nil 3.2.5 Account for effects of changes in service temperature 3.1.1.8 Nil Nil 3.2.6 Provision of means of accounting for consumed fatigue life 3.1.1.9 Nil Nil 3.2.7 Preparation and maintenance of fatigue type record

MATERIAL SELECTION 3.1.1.10 Nil Nil 3.2.8 Substantiation to account for variation in defined properties 3.1.1.11 Nil Nil 3.2.9 Material selection criteria 3.1.1.12 Nil Nil 3.2.10 Requirements for structures and assemblies

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SAFE LIFE SUBSTANTIATION 3.1.1.13 Nil Nil 3.2.11 Safe life demonstration using design spectrum 3.1.1.14 Nil Nil 3.2.12 Recording of evidence supporting the safe life 3.1.1.15 Nil Nil 3.2.13 Pre-production testing 3.1.1.16 Nil Nil 3.2.14 Testing of production standard structures using the service spectrum

RESIDUAL STRENGTH 3.1.1.17 Nil Nil 3.2.15 Demonstration of residual strength following fatigue testing 3.1.1.18 Nil Nil 3.2.16 Tear down inspection of built up structure

INSPECTION-BASED SUBSTANTIATION 3.1.1.19 Nil Nil 3.2.17 Minimum required safe life of inspection dependent components 3.1.1.20 Nil Nil 3.2.18 Recording of evidence supporting safe life 3.1.1.21 Nil Nil 3.2.19 Supporting evidence for inspection periodicity 3.1.1.22 Nil Nil 3.2.20 Effect of structurally acceptable cracks on vital services

SERVICE MONITORING 3.1.1.23 Nil Nil 3.2.21 Provision of instrumentation to estimate fatigue life consumption 3.1.1.24 Nil Nil 3.2.22 Requirement for additional instrumentation

FATIGUE LOAD METER INSTALLATIONS 3.1.1.25 Nil Nil 3.2.23 Previous location of this requirement

GENERAL REQUIREMENTS 3.1.1.26 Nil Nil 3.2.24 Provision for fatigue load meter on every aeroplane

INSTALLATION OF RAE FATIGUE LOAD METERS 3.1.1.27 Nil Nil 3.2.25 Location of meter 3.1.1.28 Nil Nil 3.2.26 Position of counter display

SWITCHING ON AND OFF 3.1.1.29 Nil Nil 3.2.27 Automatic starting and stopping

RELIABILITY 3.1.1.30 Nil Nil 3.2.28 Acceptable failure rate for fatigue meter system 3.1.1.31 201 L1 Nil 3.1.1.32 201 L2 S3/L34 Fatigue - Material selection 3.1.1.33 201 L3 S3/L35 Fatigue - Safe-life substantiation 3.1.1.34 201 L4 S3/L36 Fatigue - Inspection-based substantiation 3.1.1.35 201 L5 S3/L37 Fatigue - Testing 3.1.1.36 201 L6 S3/L38 Fatigue - Service monitoring 3.1.1.37 201 L7 S3/L39 Fatigue - Life extension 3.1.1.38 201 L8 Nil 3.1.1.39 Nil Nil S3/L40 Fatigue - Fibre-composite components 3.1.1.40 Nil Nil S3/L41 Fatigue load meter installations- General considerations

3.1.2 Processes And Working Of Materials 3.1.2.1 402 4 4.6.6 Need for flaw detection

3.2 Specific Structures 3.2.1 Radomes

3.2.1.1 210 1 6.1.31 Radome shape 3.2.1.2 210 2 6.1.32 Structural soundness of radomes 3.2.1.3 210 L0 S6/L0 References

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3.2.2 Pressure Cabins 3.2.2.1 716 12 3.7.39 Requirement to conduct fatigue analysis

FATIGUE TEST 3.2.2.2 716 14 3.7.45 Fatigue test of pressure cabin 3.2.2.3 716 14 3.7.46 Fatigue test of pressurisation systems 3.2.2.4 716 L1 S3/L13 Pressure cabins - Strength testing


3.3.1.1 1000 7 1.2.9 Responsibility for conducting flight tests 3.3.1.2 1000 7 1.2.10 Specification of limitations prior to flight testing

3.3.2 Structures FLIGHT TESTING

3.3.2.1 1015 1 3.1.17 Scope BASIC REQUIREMENTS

3.3.2.2 1015 2 3.1.18 Agreement on scope of load measurement programme 3.3.2.3 1015 2 3.1.19 Co-ordination of load measurement programme

APPLICABILITY 3.3.2.4 1015 3 3.1.20 Type of aeroplane on which tests are to be conducted

TEST REQUIREMENTS 3.3.2.5 1015 4 3.1.21 Required measurements and conditions 3.3.2.6 1015 4 3.1.22 Demonstration of structural strength

MEASUREMENTS 3.3.2.7 1015 5 3.1.23 Number and location of measurement points 3.3.2.8 1015 5 3.1.24 Temperature measurement 3.3.2.9 1015 5 3.1.25 Measurement of aeroelastic distortion and modes of vibration

3.3.2.10 1015 5 3.1.26 Recording of flight parameters FLIGHT LIMITATIONS AND THE RELATION BETWEEN STATIC STRENGTH TESTS AND FLIGHT TESTS 3.3.2.11 1015 6 3.1.27 Phasing of flight and static strength programmes 3.3.2.12 1015 6 3.1.28 Limitations for flight testing developmental aeroplanes 3.3.2.13 1015 6 3.1.29 Adjustment of ground testing on basis of flight test measurements 3.3.2.14 1015 6 3.1.30 Incorporation of structural alterations fund necessary from static tests 3.3.2.15 1015 6 3.1.31 Timing of tests required in 3.1.22 3.3.2.16 1015 L1 S3/L6 Structures - General information

4. PROOF OF STRUCTURE - FLUTTER Aim: To ensure that the structure does not suffer from flutter or other deleterious aeroelastic

mechanisms during service. Compliance: Typically by analysis supported by tests or by test at the coupon, element or subcomponent

level. The effect of repeated loading and environmental exposure on stiffness, mass and damping properties should be considered.

4.1 General Requirements 4.1.1 Aero-Elasticity

4.1.1.1 500 1 4.8.1 Scope

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EFFECT OF STRUCTURAL DISTORTION ON THE LOADS ON THE AEROPLANE 4.1.1.2 500 2 4.8.2 Allowance for aeroplane flexibility in Section 3 calculations

EFFECT OF STRUCTURAL DISTORTION ON THE STABILITY AND CONTROL OF THE AEROPLANE

4.1.1.3 500 3 4.8.3 Allowance for aeroplane flexibility in Section 2 & 6.5 calculations FLUTTER

4.1.1.4 500 4 4.8.4 Freedom from flutter STATE OF THE AEROPLANE MASS DISTRIBUTION AND STRUCTURE

4.1.1.5 500 5 4.8.5 Conditions under which 4.8.[2-4] are to be met SYSTEMS

4.1.1.6 500 5 4.8.6 Condition of systems under which 4.8.[2-4] are to be met EFFECT OF FAILURES STRUCTURE

4.1.1.7 500 6 4.8.7 Conditions under which 4.8.[2-4] are to be met for damage tolerant structure

SYSTEMS 4.1.1.8 500 6 4.8.8 Conditions under which 4.8.4 are to be met for failed systems

DEMONSTRATION OF COMPLIANCE 4.1.1.9 500 7 4.8.9 Calculations and tests to demonstrate compliance with 4.8.4

4.1.1.10 500 L1 S4/L23 Aero-elasticity Flutter clearance programme 4.1.1.11 500 L2 S4/L24 Aero-elasticity Main surface flutter 4.1.1.12 500 L3 S4/L25 Aero-elasticity Flutter of control surfaces (ailerons, elevators and

rudders) 4.1.1.13 500 L6 S4/L28 Aero-elasticity Stiffness tests

4.1.2 Active Control Systems 4.1.2.1 208 1 3.10.1 Scope

GENERAL REQUIREMENTS INTEGRATED SYSTEMS

4.1.2.2 208 1 3.10.2 Effects of associated systems on integrity of full-time ACS APPLICATIONS

4.1.2.3 208 1 3.10.3 Aim of full-time ACS FUNCTIONAL REQUIREMENTS

4.1.2.4 208 1 3.10.4 Performance requirements AIRFRAME ASPECTS GENERAL

4.1.2.5 208 4 3.10.54 Guidance regarding interaction between airframe and ACS design STRUCTURAL IMPLICATIONS

4.1.2.6 208 4 3.10.55 Factors for consideration when determining structural integrity 4.1.2.7 208 4 3.10.56 Limit load cases following ACS failure 4.1.2.8 208 4 3.10.57 Failure warning system

INTEGRITY OF THE ACTIVE CONTROL SYSTEM 4.1.2.9 208 4 3.10.58 Structural weight versus reliability of ACS considerations

DESIGN CASES 4.1.2.10 208 4 3.10.59 Principles for deriving critical design load cases

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LOADS MEASUREMENT 4.1.2.11 208 4 3.10.60 Requirements for prototype, development and preproduction aeroplanes 4.1.2.12 208 4 3.10.61 Requirements for in-service aeroplanes

MODIFICATIONS TO SOFTWARE AND HARDWARE 4.1.2.13 208 4 3.10.62 Requirements for approval of changes to ACS software or hardware

APPLICATIONS INTRODUCTION 4.1.2.14 208 7 3.10.94 Saturation characteristics of flight critical systems 4.1.2.15 208 7 3.10.95 Compatibility of systems 4.1.2.16 208 7 3.10.96 Requirements for systems which allow selection of the control mode 4.1.2.17 208 7 3.10.97 Provision for pilot override

ACTIVE FLUTTER CONTROL (AFC) 4.1.2.18 208 7 3.10.98 Aim of the system 4.1.2.19 208 7 3.10.99 Requirement to recover following failure of AFC

MANOEUVRE LOAD ALLEVIATION (MLA) 4.1.2.20 208 7 3.10.100 Requirement for effect of MLA on structural integrity

GUST LOAD ALLEVIATION (GLA) 4.1.2.21 208 7 3.10.101 To be completed

WING CAMBER CONTROL (WCC) 4.1.2.22 208 7 3.10.102 Recovery requirements

STALL AND SPIN PREVENTION (SSP) 4.1.2.23 208 7 3.10.103 Determination of post departure and recovery characteristics

STRUCTURAL LOAD LIMITING (SLL) 4.1.2.24 208 7 3.10.104 Requirement for pilot control

VARIABLE CONFIGURATION CONTROL (VCC) 4.1.2.25 208 7 3.10.105 Requirement for failsafe reversion to manual control 4.1.2.26 208 7 3.10.106 Presentation of configuration data to pilot

RIDE CONTROL (RC) 4.1.2.27 208 7 3.10.107 Compliance requirements and guidance on aim of requirement 4.1.2.28 208 L4 S3/L28 Active control systems - Structural implications of ACS

4.2 Specific Structures 4.2.1 Radio And Radar Installations

AERIAL DESIGN 4.2.1.1 708 2 6.1.18 Electrical performance considerations 4.2.1.2 708 2 6.1.19 Mechanical performance considerations



4.3.1.1 1000 1 1.2.1 Scope 4.3.1.2 1000 2 Deleted

APPLICABILITY 4.3.1.3 1000 3 1.2.2 Applicability of tests 4.3.1.4 1000 3 1.2.3 Standard of systems

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LOADING 4.3.1.5 1000 5 1.2.7 Loading and centre of gravity requirements for tests

GENERAL TEST CONDITIONS 4.3.1.6 1000 6 1.2.8 Location of specifications for each test clause

TESTS 4.3.1.7 1000 7 1.2.9 Responsibility for conducting flight tests 4.3.1.8 1000 7 1.2.10 Specification of limitations prior to flight testing

4.3.2 Flutter And Vibration 4.3.2.1 1016 1 4.8.1 Scope

FLUTTER AND VIBRATION 4.3.2.2 1016 1 4.8.10 Purpose of flight flutter tests and flight vibration study

FLIGHT FLUTTER TESTING 4.3.2.3 1016 2 4.8.11 Sequence of flight testing

FLIGHT VIBRATION STUDY 4.3.2.4 1016 2 4.8.12 Envelope of the flight vibration study 4.3.2.5 1016 L1 S4/L32 Flutter and vibration Fight vibration survey

ADDITIONAL CONSIDERATIONS 5. IMPACT DYNAMICS

Aim: To assure that occupants have every reasonable chance of escaping serious injury under realistic and survival impact conditions.

Compliance: By test or by analysis supported by test. Validated analytical techniques may be used to reduce the extent of testing.

5.1 General Requirements 5.1.1 Reduction Of Vulnerability To Battle Damage

INTRODUCTION 5.1.1.1 112 1 9.9.1 Purpose of the clause 5.1.1.2 112 1 9.9.2 Location of background information 5.1.1.3 112 1 9.9.3 Data regarding defined threat events 5.1.1.4 112 2 9.9.5 Location of definitions

DESIGN 5.1.1.5 112 3 9.9.6 Degradation due to single threat events

VULNERABILITY ANALYSIS 5.1.1.6 112 4 9.9.7 Method to determine vulnerability standards

BATTLE DAMAGE REPAIR 5.1.1.7 112 5 9.9.8 Consideration and provision for battle damage repair 5.1.1.8 112 L1 S9/L22 Reduction of vulnerability to battle damage General requirements

5.1.2 Protection of Aircrews Against Conventional Weapons GENERAL

5.1.2.1 114 1 9.10.1 Requirements 5.1.2.2 114 1 9.10.2 Scope

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DESIGN 5.1.2.3 114 2 9.10.3 Shielding of crew by structure 5.1.2.4 114 2 9.10.4 Separation of multiple pilot stations 5.1.2.5 114 2 9.10.5 Mobility and vision restrictions 5.1.2.6 114 2 9.10.6 Interference during exit, escape and crash landing 5.1.2.7 114 2 9.10.7 Selection of materials 5.1.2.8 114 2 9.10.8 Requirement for Casualty Reduction Analysis

ARMOUR 5.1.2.9 114 3 9.10.9 Requirements for armour

REDUCTION OF VULNERABILITY TO BATTLE DAMAGE 5.1.2.10 114 4 9.10.10 Notification of required protective equipment 5.1.2.11 114 L1 S9/L23 Protection of aircrew against conventional weapons General

requirements

5.1.3 Airframe Design To Resist Birdstrike Damage 5.1.3.1 209 1 4.9.1 Scope

BASIC OPERATIONAL REQUIREMENTS FLYING QUALITIES

5.1.3.2 209 2 4.9.3 Degradation of flight due to single birdstrike THE THREAT

5.1.3.3 209 3 4.9.4 Broad description of threat 5.1.3.4 209 3 4.9.5 Location of birdstrike

DETAILED REQUIREMENTS TRANSPARENCIES AND THEIR SUPPORTING STRUCTURE

5.1.3.5 209 4 4.9.6 Requirements for transparencies for defined impacts 5.1.3.6 209 4 4.9.7 Requirements for transparency support structure for defined impacts

FRONT FUSELAGE 5.1.3.7 209 4 4.9.8 Requirements for front fuselage for defined impacts

ENGINE AIR INTAKES 5.1.3.8 209 4 4.9.9 Requirements for engine air intakes for defined impacts

FRONTAL ASPECTS OF FLYING SURFACES 5.1.3.9 209 4 4.9.10 Requirements for frontal aspects of flying surfaces for defined impacts

AERODYNAMIC DEVICES ON LEADING EDGES OF FLYING SURFACES 5.1.3.10 209 4 4.9.11 Consideration of effects of birdstrike on forward facing aerodynamic

devices SYSTEMS 5.1.3.11 209 4 4.9.12 Requirements for systems dor defined impacts

GENERAL 5.1.3.12 209 5 4.9.2 Establishing mode and extent of testing

5.1.4 Crash Landing, Ditching and Precautionary Alighting on Water 5.1.4.1 307 1 4.22.1 Category of aeroplane and purpose of requirements

GENERAL 5.1.4.2 307 1 4.22.2 Overall design approach

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DESIGN FOR CRASH LANDING, DITCHING AND PRECAUTIONARY ALIGHTING ON WATER EVACUATION

5.1.4.3 307 2 4.22.3 Time and available exit limits for evacuation 5.1.4.4 307 2 4.22.4 Means of opening emergency exits 5.1.4.5 307 2 4.22.5 Continued functioning of required systems 5.1.4.6 307 2 4.22.6 Strength requirements for structure controlling use of emergency exits 5.1.4.7 307 2 4.22.7 Interference from seats, stretchers and their support structure 5.1.4.8 307 2 4.22.8 Crashworthiness of defined items

PROTECTIVE SHELL 5.1.4.9 307 2 4.22.9 Prevention of buckling of crew and passenger compartments

5.1.4.10 307 2 4.22.10 Design of interior of protective shell to minimise injury 5.1.4.11 307 2 4.22.11 Design to prevent entrapment 5.1.4.12 307 2 4.22.12 Movement of parts near occupants 5.1.4.13 307 2 4.22.13 Prevention of ceiling collapse

STRENGTH AND ENERGY ABSORPTION 5.1.4.14 307 2 4.22.14 Mass condition for strength requirements 5.1.4.15 307 2 4.22.15 Requirements for acceleration of crew upon defined impacts 5.1.4.16 307 2 4.22.16 Minimum ultimate factors for defined conditions

MATERIALS 5.1.4.17 307 2 4.22.17 Considerations for composite materials 5.1.4.18 307 2 4.22.18 Considerations for materials that may contact the ground in a crash 5.1.4.19 307 2 4.22.19 Consideration of resistance to burning and requirement of 4.26

CONTROLS 5.1.4.20 307 2 4.22.20 Prevention of hazard to crew

DESIGN FOR DITCHING AND PRECAUTIONARY ALIGHTING ON WATER GENERAL 5.1.4.21 307 3 4.22.21 Estimation of velocity and acceleration ellipsoids 5.1.4.22 307 3 4.22.22 Controlled fuel jettison

FLOTATION 5.1.4.23 307 3 4.22.23 Requirement to remain afloat 5.1.4.24 307 3 4.22.24 Requirement to remain afloat with failures in flotation aids

ESCAPE 5.1.4.25 307 3 4.22.25 Requirement to withstand local pressures upon contact with water 5.1.4.26 307 3 4.22.26 Design for salvage of equipment, deployment and entry to liferafts 5.1.4.27 307 3 4.22.27 Provision of external and internal release of liferafts

DESIGN FOR CRASH LANDING GENERAL 5.1.4.28 307 4 4.22.28 Additional requirements for category B aeroplanes

DESIGN FOR LONGITUDINAL IMPACT 5.1.4.29 307 4 4.22.29 Case 1 5.1.4.30 307 4 4.22.30 Case 2 5.1.4.31 307 4 4.22.31 Case 3

DESIGN FOR VERTICAL IMPACT 5.1.4.32 307 4 4.22.32 Case 1 5.1.4.33 307 4 4.22.33 Case 2 5.1.4.34 307 4 4.22.34 Case 3

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DESIGN FOR LATERAL IMPACT 5.1.4.35 307 4 4.22.35 Requirement for lateral impact

COMBINED CASES 5.1.4.36 307 4 4.22.36 Case 1 5.1.4.37 307 4 4.22.37 Case 2

ROLL-OVER 5.1.4.38 307 4 4.22.38 Case 1 5.1.4.39 307 4 4.22.39 Case 2 5.1.4.40 307 4 4.22.40 Case 3 5.1.4.41 307 4 4.22.41 Defined mass for Case 1 and Case 2

SEAT INSTALLATION - CREW AND SPECIFIED OCCUPANTS 5.1.4.42 307 4 4.22.42 Requirements for seat installations

SEAT INSTALLATION - OTHER OCCUPANTS 5.1.4.43 307 4 4.22.43 Requirements for seat installations for other occupants

EQUIPMENT AND COMPONENTS OF SYSTEMS 5.1.4.44 307 4 4.22.44 Restraint of equipment and components 5.1.4.45 307 4 4.22.45 Defined equipment also to meet 4.22.44 5.1.4.46 307 4 4.22.46 Requirements for stowage spaces 5.1.4.47 307 4 4.22.47 Load factors for installations where 4.22.[44-45] do not apply

CARGO AND FREIGHT 5.1.4.48 307 4 4.22.48 Requirements for support and energy absorption 5.1.4.49 307 4 4.22.49 Static strength requirements

MOUNTINGS OF MASSIVE PARTS 5.1.4.50 307 4 4.22.50 Normal and special flight case for massive parts 5.1.4.51 307 4 4.22.51 Additional requirements for parts in crash landing or ditching

STRETCHERS (LITTERS) 5.1.4.52 307 4 4.22.52 Static strength requirements for crash landing and ditching

HAND GRIPS 5.1.4.53 307 4 4.22.53 Ultimate factor for hand grips

HARNESS ATTACHMENT 5.1.4.54 307 4 4.22.54 Allowances for seat movement when harness attached to structure

EVACUATION 5.1.4.55 307 4 4.22.55 Requirements for emergency exits and related structure 5.1.4.56 307 4 4.22.56 Crashworthiness of lighting, escape identifications and markings

DESIGN OF SYSTEMS GENERAL 5.1.4.57 307 5 4.22.57 Minimise probability of fire by meeting requirements of 4.26 5.1.4.58 307 5 4.22.58 All components to meet 4.22.44 or 4.2.47 as appropriate

FUEL SYSTEM 5.1.4.59 307 5 4.22.59 Design to contain fuel during and after the crash 5.1.4.60 307 5 4.22.60 Requirements for fuel tanks

VALIDATION OF DESIGN 5.1.4.61 307 6 4.22.61 Demonstration of compliance of 4.22.[1-60] 5.1.4.62 307 6 4.22.62 Consideration of models and dynamic tests 5.1.4.63 307 6 4.22.63 Proper function when individual crashworthy elements are combined 5.1.4.64 307 6 4.22.64 Test program for ditching or precautionary alighting on water 5.1.4.65 307 6 4.22.65 Sled testing of defined structure

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RELIABILITY 5.1.4.66 307 7 4.22.66 Requirement for reliability tests

APPLICABILITY OF TABLES TABLES 30 TO 37 5.1.4.67 307 8 4.22.67 As appropriate for A and C but mandatory for new Cat. B aeroplanes

TABLE 38 5.1.4.68 307 8 4.22.68 Meteorological data

TABLES 39 TO 42 5.1.4.69 307 8 4.22.69 All categories where full standard of 4.22.[1-60] is not required 5.1.4.70 307 L0 S4/L0 References 5.1.4.71 307 L1 Part 0 Procedures for use, content and definitions 5.1.4.72 307 L2 S4/L75 Crash landing, ditching and precautionary alighting on water Design for

crash landing and ditching

5.1.5 General Detail Design 5.1.5.1 400 13 4.1.40 Material repairability and resistance to NBC attack 5.1.5.2 400 13 4.1.41 Repairable materials 5.1.5.3 400 13 4.1.42 Response to NBC effects 5.1.5.4 400 L0 S6/L0 References

5.1.6 Ice Protection OPERATIONAL REQUIREMENTS

5.1.6.1 712 2 6.9.2 Requirements for operation under defined conditions SYSTEM REQUIREMENTS - GENERAL

5.1.6.2 712 5 6.9.3 Provision of symmetric shedding 5.1.6.3 712 5 6.9.12 Effects of shed ice or slush

DESIGN AND CONSTRUCTION 5.1.6.4 712 9 6.9.29 Requirements of ice protection system

TESTING 5.1.6.5 712 9 6.9.37 Quality of ice protection system under test

5.1.7 Protection From The Effects Of Nuclear Explosions, Laser Weapons, Chemical And Biological Warfare Agents

INTRODUCTION 5.1.7.1 723 1 9.11.1 Applicability of clauses 5.1.7.2 723 1 9.11.2 Requirements for NBC/laser hardening 5.1.7.3 723 1 9.11.3 Security classification of references

GENERAL 5.1.7.4 723 2 9.11.4 Operation by personnel in NBC and laser protective clothing 5.1.7.5 723 2 9.11.5 Maintenance, replenishment and rearmament in NBC clothing

NUCLEAR ENVIRONMENT REQUIREMENTS GENERAL

5.1.7.6 723 3 9.11.6 Aim of basis nuclear survivability DESIGN

5.1.7.7 723 3 9.11.7 Design objective for nuclear hardening 5.1.7.8 723 3 9.11.8 Principal design aim 5.1.7.9 723 3 9.11.9 Initial feasibility study

5.1.7.10 723 3 9.11.10 Consideration of effects of friendly forces weapons

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OPERATIONAL CONDITIONS 5.1.7.11 723 3 9.11.11 Flight and ground conditions at exposure

CHEMICAL AND BIOLOGICAL ENVIRONMENT REQUIREMENTS GENERAL 5.1.7.12 723 4 9.11.12 Determination of level of chemical hardening

DESIGN 5.1.7.13 723 4 9.11.13 Design objective 5.1.7.14 723 4 9.11.14 Principal design aim 5.1.7.15 723 4 9.11.15 Repeated operation while contaminated 5.1.7.16 723 4 9.11.16 Design for resistance to attack 5.1.7.17 723 4 9.11.17 Design for handling and decontamination 5.1.7.18 723 4 9.11.18 Requirement for Chemical and Biological survivability feasibility study 5.1.7.19 723 4 9.11.19 Design for prevention of ingress of liquid chemical agents 5.1.7.20 723 4 9.11.20 Design criteria for environmental control system 5.1.7.21 723 4 9.11.21 Use of all weather seals to preclude CW or BW contaminants 5.1.7.22 723 4 9.11.22 Suitable filtration 5.1.7.23 723 4 9.11.23 Requirements for materials liable to contamination

CHEMICAL AND BIOLOGICAL TESTING 5.1.7.24 723 4 9.11.24 Provision of materials proposed for defined uses

LASER REQUIREMENTS GENERAL 5.1.7.25 723 5 9.11.25 Developments of lasers 5.1.7.26 723 5 9.11.26 Aim for laser survivability

DESIGN 5.1.7.27 723 5 9.11.27 Design objective for laser hardening 5.1.7.28 723 5 9.11.28 Principal design aim 5.1.7.29 723 5 9.11.29 Conduct laser survivability study during feasibility study stage 5.1.7.30 723 5 9.11.30 Minimisation of damage due to friendly forces 5.1.7.31 723 L0 S9/L0 References 5.1.7.32 723 L1 S9/L24 Protection from the effects of nuclear explosions, laser weapons, chemical

and biological warfare agents -Definitions



5.2.2 Radio And Radar Installations 5.2.2.1 708 1 6.1.1 Scope

RADIO AND RADAR EQUIPMENTS 5.2.2.2 708 1 6.1.2 Performance of installations 5.2.2.3 708 1 6.1.3 Proof and ultimate factors

AERIAL LOCATION ON AN AIRFRAME 5.2.2.4 708 3 6.1.20 Electrical performance considerations

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MECHANICAL CONSTRAINTS 5.2.2.5 708 3 6.1.21 Fail safe design of mechanically deployed aerials 5.2.2.6 708 3 6.1.22 Defined mechanical constraints

RADOMES AND AERIAL FAIRINGS MECHANICAL/REQUIREMENTS

5.2.2.7 708 5 6.1.31 Radome shape 5.2.2.8 708 5 6.1.32 Structural soundness of radomes 5.2.2.9 708 5 6.1.33 Lightning protection of radome fairings


TESTING 5.2.2.12 708 9 6.1.47 Conduct of flight and ground testing

6. FLAMMABILITY Aim: To minimise the hazard to occupants if flammable liquids are ignited and for components to

withstand exposure to heat, flames or sparks. The use of composites should not reduce the level of safety inherent in conventional metallic structure.

Compliance: By analysis supported by test. A test has been developed for evaluating the flammability of materials that are required to be fire resistant in civilian aircraft (AC 20-107A Section 9. b. (2)).

6.1 General Requirements 6.1.1 Fire Precautions

6.1.1.1 713 1 4.26.1 Scope GENERAL REQUIREMENTS

6.1.1.2 713 2 4.26.2 Designation of fire zones 6.1.1.3 713 2 4.26.3 Risk of spontaneous ignition and provision of warning systems 6.1.1.4 713 2 4.26.4 Minimising ignition risk from leakage of flammable fluids 6.1.1.5 713 2 4.26.5 Fire detection and suppression equipment in designated fire zones 6.1.1.6 713 2 4.26.6 Routing of essential flight controls and services 6.1.1.7 713 2 4.26.7 Design of filling points for flammable fluids 6.1.1.8 713 2 4.26.8 Ducting and discharge of cooling air 6.1.1.9 713 2 4.26.9 Design of fire extinguisher system

6.1.1.10 713 2 4.26.10 Electrical cables and terminals in designated fire zones PRECAUTIONS IN DESIGNATED FIRE ZONES 6.1.1.11 713 3 4.26.11 Listing of, and requirements for, designated fire zones 6.1.1.12 713 3 4.26.12 Fires in multi-engine aeroplanes

TORCHING FLAMES 6.1.1.13 713 3 4.26.13 Precaution to protect aeroplane from the effects of torching flames

FLAMMABLE FLUID SYSTEMS 6.1.1.14 713 3 4.26.14 Proximity of ignition sources to systems carrying flammable fluids 6.1.1.15 713 3 4.26.15 Protection of components carrying flammable fluids 6.1.1.16 713 3 4.26.16 Protection of parts in designated fire zones 6.1.1.17 713 3 4.26.17 Location and protection of flammable fluid tanks 6.1.1.18 713 3 4.26.18 Treatment of absorbent materials near flammable fluid systems

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DRAINS, VENTS AND VENTILATION 6.1.1.19 713 3 4.26.19 Drainage requirements for designated fire zones 6.1.1.20 713 3 4.26.20 Ventilation requirements for designated fire zones

FLAMMABLE FLUID SHUT-OFF 6.1.1.21 713 3 4.26.21 Shut-off of flammable fluids through designated fire zones

FIREWALLS 6.1.1.22 713 3 4.26.22 Parts that must be isolated by firewalls 6.1.1.23 713 3 4.26.23 Requirements of systems passing through firewalls

FIRE DETECTION AND FIRE WARNING 6.1.1.24 713 3 4.26.24 Requirements for fire/temperature detectors in designated fire zones

FIRE EXTINCTION 6.1.1.25 713 3 4.26.25 Location of fire extinguishing systems 6.1.1.26 713 3 4.26.26 Zones that require second discharge of extinguishant 6.1.1.27 713 3 4.26.27 Systems for APU, fuel burning heater and combustion equipment 6.1.1.28 713 3 4.26.28 Operation of main engine power unit extinguisher systems 6.1.1.29 713 3 4.26.29 Operation of fire extinguishing system under crash conditions 6.1.1.30 713 3 4.26.30 Detector to show that extinguishant has been discharged

PRECAUTIONS IN OTHER ZONES 6.1.1.31 713 4 4.26.31 Cross-reference to clauses for precautions related to combat fires

FLAMMABLE FLUID FIRE PROTECTION 6.1.1.32 713 4 4.26.32 Minimising probability of ignition of leaked flammable fluids 6.1.1.33 713 4 4.26.33 Means of alerting crew if crew action is required 6.1.1.34 713 4 4.26.34 Identification of areas where flammable fluids may leak 6.1.1.35 713 4 4.26.35 Cross-reference to requirements for fluid drains, vents and ventilation 6.1.1.36 713 4 4.26.36 Location of vent or drainage provision

AREAS ADJACENT TO DESIGNATED FIRE ZONES AND ENGINE NACELLE ATTACHING STRUCTURES 6.1.1.37 713 4 4.26.37 Cross-reference to requirements for relevant structure 6.1.1.38 713 4 4.26.38 Construction of engine mountings and other critical structure 6.1.1.39 713 4 4.26.39 Requirement for components and structure immediately adjacent to

firewalls 6.1.1.40 713 4 4.26.40 Airspace requirements between firewalls and tanks or reservoirs

ELECTRICAL SYSTEM FIRE AND SMOKE PROTECTION 6.1.1.41 713 6 4.26.46 Requirements for electrical components 6.1.1.42 713 6 4.26.47 Requirements in event of failure of electrical equipment 6.1.1.43 713 6 4.26.48 Electrical equipment that may come into contact with flammable vapours 6.1.1.44 713 6 4.26.49 Flammability requirements for insulated electrical wire and cable

CARGO BAYS 6.1.1.45 713 8 4.26.56 Location and protection of safety critical parts 6.1.1.46 713 8 4.26.57 Protection of fire-fighting features in compartments 6.1.1.47 713 8 4.26.58 Shielding or insulation of heats sources 6.1.1.48 713 8 4.26.59 Cross-reference to classification of cargo compartments 6.1.1.49 713 8 4.26.60 Requirements for compartments required to contain a fire detection

system PRECAUTIONS: COMBAT INDUCED FIRES 6.1.1.50 713 11 4.26.71 Design and location of components 6.1.1.51 713 11 4.26.72 Routing of fuel lines 6.1.1.52 713 11 4.26.73 Draining and venting of fuel tanks located above engines

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COMPARTMENT INTERIORS - TEST CRITERIA 6.1.1.53 713 12 4.26.74 Cross-reference to requirements for materials used in inhabited

compartments 6.1.1.54 713 12 4.26.75 Group #1. Self extinguishing when tested vertically 6.1.1.55 713 12 4.26.76 Group #2. Self extinguishing when tested vertically 6.1.1.56 713 12 4.26.77 Group #3. Defined burn rate when tested horizontally 6.1.1.57 713 12 4.26.78 Other materials 6.1.1.58 713 12 4.26.79 Additional requirements for seat cushions 6.1.1.59 713 L0 S4/L0 References 6.1.1.60 713 L1 Part 0 Procedures for use, content and definitions 6.1.1.61 713 L2 S4/L86 Fire precautions General recommendations 6.1.1.62 713 L3 S4/L87 Fire precautions Combat induced fires 6.1.1.63 713 L4 S4/L88 Fire precautions An acceptable test procedure for showing compliance

with Clause 4.26.74-81

6.1.2 Reduction Of Vulnerability To Battle Damage INTRODUCTION

6.1.2.1 112 2 9.9.5 Location of definitions DESIGN

6.1.2.2 112 3 9.9.6 Degradation due to single threat events VULNERABILITY ANALYSIS

6.1.2.3 112 4 9.9.7 Method to determine vulnerability standards 6.1.2.4 112 L1 S9/L22 Reduction of vulnerability to battle damage General requirements

6.1.3 Crash Landing, Ditching and Precautionary Alighting on Water GENERAL

6.1.3.1 307 5 4.22.57 Minimise probability of fire by meeting requirements of 4.26 6.1.3.2 307 5 4.22.58 All components to meet 4.22.44 or 4.2.47 as appropriate

FUEL SYSTEM 6.1.3.3 307 5 4.22.59 Design to contain fuel during and after the crash 6.1.3.4 307 5 4.22.60 Requirements for fuel tanks

7. LIGHTNING PROTECTION Aim: For the structure to dissipate P-static electrical charges and divert the resultant electrical

current so as not to endanger the aircraft. Compliance: By analysis supported by test. Consideration shall be given to possible deterioration and

undetected damage of the lightning protection system.

7.1 General Requirements 7.1.1 Bonding And Screening

7.1.1.1 709 1 4.27.1 Scope of clauses and purpose of bonding BONDING

7.1.1.2 709 3 4.27.7 Bonding requirements for metallic parts of structure and skin 7.1.1.3 709 3 4.27.8 Consideration of bonding for non-metallic parts 7.1.1.4 709 3 4.27.9 Bonding of metallic control and distribution panels 7.1.1.5 709 3 4.27.10 Bonding of the engine

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CLASS A BONDING (ANTENNA INSTALLATION) 7.1.1.6 709 3 4.27.11 General requirement for bonding 7.1.1.6 709 3 4.27.12 Bonding of hatches in vicinity of antenna 7.1.1.6 709 3 4.27.13 Circumferential RF continuity

CLASS C BONDING (CURRENT RETURN PATH) 7.1.1.6 709 3 4.27.14 Adequacy of bond to carry maximum fault current 7.1.1.6 709 3 4.27.15 Bonding in areas where hazardous conditions exist

CLASS H BONDING (SHOCK HAZARD) 7.1.1.6 709 3 4.27.16 Exposure of paths containing high voltage

CLASS R BONDING (RF POTENTIAL) 7.1.1.6 709 3 4.27.17 Bonding of equipment that emits electromagnetic energy 7.1.1.6 709 3 4.27.18 Inherent RF bonding within aeroplane design 7.1.1.6 709 3 4.27.19 Bonding of metallic equipment mountings 7.1.1.6 709 3 4.27.20 RF bonding of cable screens and connector shells

CLASS S BONDING (STATIC CHARGE) 7.1.1.6 709 3 4.27.21 Mechanically secure connections to aeroplane structure 7.1.1.6 709 3 4.27.22 Bonding of metal parts carrying fluids

LIGHTNING STRIKE PROTECTION PROTECTION - GENERAL REQUIREMENTS (CLASS L BONDING)

7.1.1.7 709 4 4.27.23 Incorporation of lightning protection measures through design stage 7.1.1.8 709 4 4.27.24 Use of, and requirements for, primary conductors 7.1.1.9 709 4 4.27.25 Compliance statement for bonding straps and soldered connections

PROTECTION OF STRUCTURE 7.1.1.10 709 4 4.27.26 Protection requirements for conventional metallic aeroplanes 7.1.1.11 709 4 4.27.27 Consideration of strike plates for non-metallic materials 7.1.1.12 709 4 4.27.28 Consideration for non-metallic structure housing electrical equipment 7.1.1.13 709 4 4.27.29 Protection of transparencies that contain electrical films or elements 7.1.1.14 709 4 4.27.30 Prevention of damage to electrical systems from induced voltages

PROTECTION OF CONTROL SURFACES AND CONTROL SYSTEMS 7.1.1.15 709 4 4.27.31 Bonding of control surfaces, flaps and any other moving parts

PROTECTION OF PROTRUSIONS AND EXTERNAL PARTS 7.1.1.16 709 4 4.27.32 Bonding of external electrically isolated conductors 7.1.1.17 709 4 4.27.33 Design of antenna systems for lightning discharge 7.1.1.18 709 4 4.27.34 Consideration of voltage spikes due to strikes on parts connected to

electrical system 7.1.1.19 709 4 4.27.33

(error) Consideration to the protection of large non-conducting projections

PROTECTION OF THE FUEL SYSTEM 7.1.1.20 709 4 4.27.35 Location and design of fuel vents and jettisoning systems 7.1.1.21 709 4 4.27.36 Consideration of main ground system in design of fuel system 7.1.1.22 709 4 4.27.37 Consideration of integral metallic wing fuel tanks 7.1.1.23 709 4 4.27.38 Metallic parts in non-metallic fuel tanks

LIGHTNING PROTECTION TESTS 7.1.1.24 709 4 4.27.39 Requirements for high current pulse tests 7.1.1.25 709 L0 S4/L0 References 7.1.1.26 709 L2 S4/L89 Bonding and screening Bonding of control surfaces 7.1.1.27 709 L3 S4/L90 Bonding and screening Recommended lightning tests

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7.1.2 Lightning Strike Protection 7.1.2.1 ADF TAR requirement - Lightning strike protection

Comply with FAA AC 20-107A, Section 9. c.


RADOMES AND AERIAL FAIRINGS MECHANICAL/REQUIREMENTS


7.2.2 Radio And Radar Installations RADOMES AND AERIAL FAIRINGS

MECHANICAL/REQUIREMENTS 7.2.2.1 708 5 6.1.31 Radome shape 7.2.2.2 708 5 6.1.32 Structural soundness of radomes 7.2.2.3 708 5 6.1.33 Lightning protection of radome fairings



8. PROTECTION OF STRUCTURE Aim: To protect the structure against the effects of weathering, abrasion, erosion, ultraviolet

radiation and chemical environment (glycol, hydraulic fluid, fuel, cleaning agents, etc.). Compliance: By test to demonstrate suitable protection against these agents, or consideration of the

degradation in material properties resulting from exposure. 8.1 General Requirements

8.1.1 General Requirements LOOSE ARTICLE HAZARDS - CONTROL SYSTEMS

8.1.1.1 100 17 1.1.29 Design to prevent generation of loose articles 8.1.1.2 100 17 1.1.30 Preservation of flying qualities in presence of jamming by loose articles 8.1.1.3 100 17 1.1.31 Requirements for guards

PREVENTION OF ACCIDENTAL DAMAGE 8.1.1.4 100 18 1.1.32 Design for prevention of accidental damage

8.1.2 Operation In Various Climatic Conditions WEATHERPROOFING WATERPROOFING

8.1.2.1 101 3 7.1.16 Weatherproofing of fuselage

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DUST AND SAND PROOFING 8.1.2.2 101 4 7.1.22 Protection against sand and dust 8.1.2.3 101 4 7.1.23 Prevention of accumulation of sand inside fuselage structure 8.1.2.4 101 4 7.1.24 Operation of hydraulic e

DSTO-TN-0498

Documents

adf comparative basis

specific adf requirements

primary structure

bonded composite repairs

bonded composite material

case basis

current aircraft

aircraft structures